Aeroplane.



A. soHRA's & 'F.QIRIARTE.

AEROPLANE.

APPLICATION FILED APR. e. 191e.

P: Ltented Feb; 20, 1917.

3 SHEETS-SHEET l 3 nnen fofz,

N 21.6% ma) @L L n s N M A. BORR/xs e F. IRIARTE.

AEROPLANE.

APPLICATION FILED APR. 8, 19| i.

1 ,216,652. Petented Feb. '20, 1917.

45 indicate the Wings, 3 indicates the propeller,

UNITED STATES PATENT OFFICE.

AEBOPLANE.

Speciflcation of Letters Pate nt.

Patented Feb. 20, 1917.

Application llled April B, 1916. Seria l No. 89,758.

To allwhomitwza1/.concern. l

le it known that we, ANTONIO BonRs and FERNANno Inrau'rE, citizens ofthe Republic o Portugal and of Argentina, re spertively. and bothresidents of the city of menos \ires, Arnentina, have invented certainne and usetillImprovements in Aeroplanes, of which the following is aspecification.

)ur invention relates to an improvement in aeroplanes and has as itsobject the provision oi' a novel control for the aeroplane rudderwhereby a single lever may be actuated to incline the rudder up O1' downor slunting sidewse'in either direction or a combination of suchmotions. By this means the. aeroplane may be directed up or down or toeither side, or directed to climb spirally in either a right or a lefthand direction or permitted to volplane downward in a similar way. f

In the following we have described, in connection with the accompanyingdrawings, a structure illustrating oneI way of earrying out ourinvention, the features thereof being ino/re particularly pointed outherein-v after in the claims.

` Tn the. drawings Figure 1 is a plan View of a, mono-plane. equippedwith a rudder and steeringr =mechal'iism embodying our invention; Fig. 2is a detail sectional view, on a slightly larger scale, of the rudderoperatingY means; Fig. 3 is a central vertical sectional, View of therear portion of the structure shown in Fig. l. parts being broken away;Fig. l is a view similar to Fig. 3 butin horizontal section; Fig. 5 is aperspective view of the steering mechanism `detached and.

Figs. (l andl 7 detail views of the steeringr mechanism. ,Y

Similar numerals of reference indicate similar parts throughouttheseveral views. l indicates the body of the aeroplane, which may be madeof any suitable light weight material such as aluminum, ete., 2, 2

parts of driven by any suitable means (not shown), 4, '-1 indicato thesik'levanes and 5 indicates the rudder. 6 indicates a. rod extendingtransversely of rudder 5 and rotatably jour'- nalod in yoke. 7. -8indicates a. ,shaft journaled in bearing.4 l) aud l0 in body 1 andattached firmly to .yoke 7, |n'el'erably as shown in Fig. 2, where yoke7 is shown as provided with a projecting portion llV over which shaft 8,here shown as hollow, lits and to Aable beari lgs in opposite sideswhich it' may bte-.fastened in any convenient way. 12, 12 indicate ballbearings on which yoke 7"t\ 'rns against bearing 10. 13 indicates a s1'rocket wheel mounted on =the end of sliaft E. 14 indicates the pit ofthe aeroplane and l5 a seat for the operator. 16 in,- dieates a leverpivoted in'strapu17 at 18. 1E), 1U indicate hollow trnnnions to whichstrap 17 is firmly attached at each end, the trunnions being rotatablymounted `in suit of the body. 20, 2() indicate. auxiliary levers ixedlymounted on trunnions` 1l), 19. 2l indicates a third al Kilian)r leverfixedly mounted on rod (i in tlze rudder. 22, 22 and 23, 23:1respectively ind rate connections between the upper ends of levers 20,2() and the upper end of lever il and vthe lower ends of levers 20,2()and the lower end of lever 21. 24 indicatesl a connection, preferably inthe form of an endl rial, fastened 'at 25 to lever L6, running through aportion'of each of hollow trunnions 19, .9, and thence over guiderollers 2G, 2G over sprocket 13. 27 indicates 'a sprocket c lain forminga part of rope 24, passing o\ er sprocket .wheel 13 4and 28 a shield toprevent disengagement of" the sprocket cl ain and wheel.

'In opentiner or directing the rudder a backward 1nd forward movement oflever' 1liw-ill raise the rlulder, through auxiliary levers 20. J and 2land connections and 23, to be lowered or raisedhorizontally, 1ever 2lbeir ,e l'ast on rod (i und rod (l being rotatably nonnted in yoke 7.Point 25, where rop( 2l is fastened to lever 1.6, and point lS wherelever 1G is pivoted to strap 17 being at silistantiallyermal distancesfrom the center et' rotation, through trunilions 1l),

1*.) extended, the turned motion moved from point 1S, tl en 'sprocket 13the rudder is caused to be raised or lowered at its ends according tothe' motion given 'zo lever 16. It will also be seen that it' the everyoke 7 is not actuated to be during.:` the lmckward` and forward oflever 1b'. But if-1evcr 16 is i then shifter` forward'orlmckwa-rd,'wldonib nation of n otions may be given to' therdder. For emmple, if thel leverlG Vis shifted backward rudder 5 will be depressedhorizontally and the air currents striking.,r against the sa me willcause the aeroplane to descend; il" the .lever is shifted forward rud- Yss llexible rope of suitable mate-` side to side upon its pivotal4through rope 24 passing over" is moved to either sidealid der will beelevated horizontallyand the f air currents striking against the samewill cause the aero lane to rise; if the lever 1s shiftedf'to the eft(in the drawing) the lever standing neutral as to rope 24-that isrudder5 being in a horizontal position, the right'hand end of the rudderwillbe depressed and the aeroplane will turn sidewise tothe right; ifthe lever is however shifted to 'the right under the i conditions lasset forth, theleft hand end of the rudder will bede ressedandl-theaeroplane will turn sidewise to the/left; if the lever 16 be shiftedbackward and tothe left, at the sameftime* the rudder. will be depressedhorizontally and depressed at the right hand,Y end, thus' permittin theaeroplane to vol-plane down'- Ward circ ing to the right. `If the leverbe shifted forward and to'the -left atthe vsame time, the rudder will`be elevated horizontally. and depressed at the right hand end and theaeroplane will climb spirally` cir-l cling to the right. If the lever 16be shifted backward and to the right at the same time, .the rudder willbe depressed horizontallyl vand depressed -at the left hand end",` thuspermitting the aeroplane to vol-plane down-'- ward circling to the left.If the lever -16 he the left. v

I shifted A:forward and to the right at the samel time, the rudder willbe elevated` horizontally and depressed at the left hand end 'and theaeroplane will climb spirally`v circling to It is-clear thatwehaveprovided a rudder 1 control wherein by a shifting of a singlecontrollever, the 4various motions of the aeree' f plane may be directed andthe aeroplane guided as vdesired.

. The particular construction and arrangement of parts is not essentialand we do not restrict ourselves to such further than the scope of theappended claims demands.-

We claim: l

- 1. In an aeroplane, a yoke rotatably carriedby the aeroplane body, arod rotatably journaled in the yoke and extending beyond the same ateach end, a* rudder mounted on said rod, a lever fixedly mounted on therod and a common operating means for con'- trolling the movement of saidyoke and rodl either simultaneously on dissimultaneously.

2. In an aeroplane, a rudder suspended to be free to move up and down'andito be tipped sideWise in. either direction, a control lever,;astrap to which said lever is piv` oted, a pair of rotatable trunnions towhich the lends`of said 'strap are fixed, auxiliary levers iixedlymounted on the trunnions, an auxiliary .lever carried by the rudder,-connections between said auxiliary levers on the trunnions and theauitiliar'y lever on the p mounted on'the rod, a' control lever and con#nections actuated-by the movement of the r control lever to move the'yokel and the auxiliary lever either simultaneously ordissimultaneously.' p y In testimony whereof we have signed thisspecification. y

- ANTONIO BORRS.

FERNANDO IRIARTE.

